JP6368544B2 - Joint assembly and its assembly method - Google Patents

Description

  The field of the invention relates generally to coupling mechanisms, and in particular to pressurized peel resistant joints used to join components together.

  At least some known aircraft components are manufactured from multi-layer laminate structures made of non-metallic composite materials such as carbon fiber reinforced polymer (CFRP). Composite materials typically have a high specific strength and can be formed in a variety of shapes and sizes. Composite materials can be used in combination with metallic materials such as aluminum, titanium, and / or steel to reduce the weight of the aircraft. The reduction in total weight usually contributes to an increase in aircraft fuel efficiency.

  One known composite component manufacturing method uses an autoclave molding procedure. Autoclave molding typically includes pre-impregnating a layer of composite reinforcing material with resin, forming the layer into the desired component shape, and placing the desired component in the autoclave. By increasing the temperature and / or pressure inside the autoclave, the resin cures and provides support to the reinforcing material, allowing the desired shape to be maintained. However, autoclaves usually require a large capital investment, require a physically large site area, and are expensive to operate.

  At least some known aircraft components made from composite materials can be bonded together using an adhesive. Adhesives are generally effective at bonding components together, but can occur during the life of an aircraft. For example, delamination can occur after prolonged use of an aircraft and / or can occur when a foreign object strikes the material during flight. Such peeling is difficult to detect during regular maintenance and difficult to detect by visual inspection.

  At least some known non-destructive inspection (NDI) techniques can be used to determine delamination between components during assembly. For example, NDI techniques include ultrasonic inspection, thermographic inspection, and / or inspection with a tap hammer. However, known NDI techniques typically provide weak and / or zero strength bonding (ie, “kissing bond”) without causing discontinuities along the bond line to facilitate detection. Such detection difficulties limit the use of weak and zero-strength bonds in certain applications, and the known NDI technology is time consuming and labor intensive. It is expensive and expensive to implement.

  In one aspect, a joint assembly is provided. The fitting assembly includes a first component and a second component, the second component extending from the first portion and the first component, wherein the second component is attached to the first component. And a plurality of flexible members configured to bend when connected. The plurality of flexible members makes it easy to limit the spread of edge separation beyond each of the plurality of flexible members.

  In one aspect, a fuselage assembly is provided. The fuselage assembly includes a first cylindrical section including a body portion extending from a first end to a second end, a body portion extending from the first end to the second end, and extending from at least one of the first end and the second end. A second cylindrical section including a plurality of flexible members, wherein the plurality of flexible members are configured to bend when connecting the second cylindrical section to the first cylindrical section. The plurality of flexible members makes it easy to limit the spread of edge separation beyond each of the plurality of flexible members.

  In yet another aspect, a method for assembling a joint is provided. The method includes providing a first component that includes a first portion and a plurality of flexible members extending from the first portion, and coupling the plurality of flexible members to the second component. . The plurality of flexible members make it easy to limit the spread of edge separation beyond each of the plurality of flexible members, and are configured to bend when connected to the second component.

  Furthermore, the present invention includes embodiments according to the following clauses.

Article 1
A first cylindrical section including a body portion extending from the first end to the second end; a body portion extending from the first end to the second end; and a plurality of flexible portions extending from at least one of the first end and the second end A plurality of flexible members, wherein the plurality of flexible members are configured to bend when connecting the second cylindrical section to the first cylindrical section, A fuselage assembly comprising a second cylindrical section that facilitates limiting edge spread beyond each of a plurality of flexible members.

Article 2
The assembly of clause 1, wherein the first cylindrical section includes a coupling surface configured to mate with the plurality of flexible members.

Article 3
The assembly of clause 1, wherein the plurality of flexible members are fabricated from a composite material.

Article 4
The plurality of flexible members become progressively thinner to facilitate improving a gradual load transition to a joint defined between the first cylindrical section and the second cylindrical section. The assembly according to Clause 1.

FIG. 2 is a flow diagram illustrating an exemplary aircraft production and maintenance method. 1 is a block diagram of an exemplary aircraft. 1 is a perspective view of an exemplary fuselage assembly. FIG. FIG. 4 is a perspective view of a section of an exemplary fitting assembly that may be used to assemble the fuselage assembly shown in FIG. 3. FIG. 5 is an exploded view of the joint assembly shown in FIG. 4. FIG. 6 is a cross-sectional view of the joint assembly shown in FIG. 5. FIG. 4 is an exploded view of an alternative joint assembly that may be used to assemble the fuselage assembly shown in FIG. 3. FIG. 8 is a cross-sectional view of the joint assembly shown in FIG. 7.

  Implementations of the invention relate to assemblies and methods that can be used to interconnect components. Specifically, the components are bonded together using an adhesive to help improve the control of the bond lines between the components and / or have the possibility of delamination along the joints formed between the components Features can be included that allow the location to be easily detected. In an exemplary implementation, at least one of the components includes a first portion and a plurality of flexible members that extend from the first portion and couple to another component. The flexible member is pressurized in a predetermined direction and bends in the predetermined direction when connected to other components. Furthermore, the flexible members are separated from each other to help limit the spread of edge separation along the joint.

  Referring now to the drawings, implementation aspects of the present invention will be described in the context of aircraft production and maintenance method 100 (FIG. 1) and aircraft 102 (FIG. 2). In the pre-production phase, including specifications and design 104 data for aircraft 102 is used during the manufacturing process and other materials associated with the fuselage are procured 106. In the manufacturing phase, component and subassembly manufacturing 108 and system integration 110 of the aircraft 102 are performed, after which the aircraft 102 enters an authorization and delivery process 112. Once the aircraft authorization has been successfully satisfied and completed, the aircraft 102 is put into service 114. While in service by a customer, the aircraft 102 is regularly subjected to routine planned maintenance and maintenance 116 (eg, including changes, reconfigurations, and / or modifications).

  Each portion and process associated with aircraft production and / or maintenance method 100 may be performed or completed by a system integrator, a third party, and / or an operator (eg, a customer). For purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and subcontractors of major systems, and third parties include, but are not limited to any number of Vendors, subcontractors, and suppliers can be included, and operators can be airlines, leasing companies, military organizations, service organizations, and the like.

  As shown in FIG. 2, the aircraft 102 manufactured by the method 100 may include a fuselage 118 having a plurality of systems 120 and an interior 122. Examples of high level system 120 include one or more of propulsion system 124, electrical system 126, hydraulic system 128, and / or environmental system 130. Any number of other systems may be included. Although an example of an aircraft has been shown, the principle of the present invention can be applied to industries other than the aircraft industry such as the automobile industry.

  The devices and methods embodied herein may be employed at any one or more of the stages of method 100. For example, the component or subassembly corresponding to the component production process 108 is made or manufactured in a manner similar to the component or subassembly that is produced during operation of the aircraft 102. Also, one or more apparatus implementations, method implementations, or combinations thereof may be used, for example, by substantially increasing the assembly of the aircraft 102 and / or reducing the assembly costs of the aircraft 102. , Can be utilized during manufacturing stages 108 and 110. Similarly, one or more of apparatus implementations, method implementations, or combinations thereof may be utilized during operation or maintenance of aircraft 102, for example, during planned maintenance and maintenance 116. Can do.

  FIG. 3 is a perspective view of an exemplary fuselage assembly 200. In the exemplary embodiment, fuselage assembly 200 includes a first cylindrical section 210 and a second cylindrical section 220. The first cylindrical section 210 includes a body 212 that extends from a first end 214 to a second end 216, and the second cylindrical section 220 includes a body 222 that extends from a first end 224 to a second end 226. Yes. In this exemplary embodiment, the second ends 216 and 226 of the first and second cylindrical sections 210 and 220 are connected to each other at a joint 230 located therebetween.

  4 is a section cross-sectional view of an exemplary joint assembly 300 used to assemble the fuselage assembly 200 (see FIG. 3), FIG. 5 is an exploded view of the joint assembly 300, and FIG. It is sectional drawing. In the exemplary implementation, the fitting assembly 300 includes a first component 310 and a second component 320 coupled to the first component 310. Specifically, the first component 310 and the second component 320 are bonded together using a layer of adhesive 340 to a joint 330 located therebetween. The first component 310 and the second component 320 can be joined by any adhesive that allows the fitting assembly 300 to function as described herein. Further, in the exemplary implementation, the second component 320 includes a bonding surface 328 for receiving an adhesive layer 340 thereon.

  In this exemplary implementation, the first component 310 includes a first portion 312 and a plurality of flexible members 314 that extend to one end 316 of the first component 310, and the second component 320 is a first component 320. And substantially the same configuration complementary to the component 310 of FIG. Thus, in the exemplary embodiment, second component 320 also includes a first portion 322 and a plurality of flexible members 324 that extend to one end 326 of second component 320. Although the first component 310 will now be described in further detail, it should be understood that the same description applies to the second component 320.

  In this exemplary implementation, the first component 310 and the second component are coupled together along the fitting 330. Specifically, the adhesive layer 340 extends to at least a portion between the first component 310 and the second component 320 to connect the first component 310 and the second component 320 to each other. Furthermore, the first portion 312 has a substantially uniform thickness T1, and the first component 310 is thinner toward the front, and the thickness decreases from the first portion 312 toward the end 316. Yes. Since the first component 310 and the second component 320 are substantially the same and complementary to each other, the fitting assembly 300 has a substantially uniform thickness along the fitting 330. For example, in this exemplary implementation, the joint 330 has a thickness T2 that is substantially the same as the thickness T1. Therefore, the thickness of the first component 310 is reduced as it goes forward, which facilitates improving the gradual load transition to the joint 310 along the longitudinal direction 350.

  In some implementations, the flexible member 314 extends from the first portion 312 and couples to the second component 320. Specifically, the flexible member 314 extends from the first portion 312 and coincides with a bonding surface 328 defined on the second component 320 and the adhesive layer 340 connects the flexible member 314 to the bonding surface 328. To do. Further, adjacent flexible members 314 are separated by slits 332 and an aperture 334 is defined therebetween. The slits 332 and the apertures 334 promote increased peel isolation along the joint 330 by limiting the spread of edge separation beyond each flexible member 314. Specifically, in this exemplary implementation, each flexible member 314 is isolated from the adjacent flexible member 314 by extending the slit 332 to the edge 316 of the first component 310. By isolating the flexible member 314, it is easier to limit the spread of separation from propagating along the joint 330 in the lateral direction 352. Also, isolating the flexible members 314 allows each flexible member 314 to compensate for irregularities and / or distortions in the coupling surface 328 of the second component 320.

  In some implementations, the flexible member 314 facilitates smooth load transitions and reduction of stress conditions along the joint 330. For example, the axial load within the flexible member 314 extends in the longitudinal direction 350 and the off-axis load within the flexible member 314 extends in the lateral direction 352. Segmenting the flexible member 314 may make it difficult for the flexible member 314 to handle off-axis loads along the joint 330. Therefore, the coupling is strengthened along the joint 330 due to improved load transition and reduced stress state in the flexible member 314.

  The flexible member 314 can be made from any material that allows the fitting assembly 300 to function as described herein. Exemplary materials include, but are not limited to, composite materials such as carbon fiber reinforced polymer (CFRP). Further, the flexible member 314 is pressurized in a predetermined direction before being coupled to the second component 320. Specifically, the flexible member 314 is pressurized in a predetermined direction toward the second component 320 or in a predetermined direction away from the second component 320. Next, the flexible member 314 bends in a direction opposite to a predetermined direction when the first component 310 and the second component are connected to each other.

  In one implementation, the flexible member 314 is pressurized in a predetermined direction 354 prior to being coupled to the second component 320. Specifically, the flexible member 314 is bent toward the second component 320 to pressurize in a predetermined direction 354. The flexible member 314 then bends away from the second component 320 in a direction 356 opposite the predetermined direction 354 when the first component 310 and the second component are coupled together. Thus, the flexible member 314 that bends in the opposite direction 356 defines a tensile surface 336 and a compression surface 338 opposite the tensile surface 336 on the first component 310. The tensile surface 336 is then coupled to the second component 320 via the adhesive layer 340.

  In one implementation, the flexible member 314 facilitates a reduction in the application of a load to the entire flexible member 314 necessary to achieve sufficient coupling along the joint 330 and / or a bond along the joint 330. Easy to improve line control. For example, in one implementation, the additional load provided by the pressurized flexible member 314 may couple the first component 310 and the second component 320 without using an autoclave (not shown). to enable. Specifically, the adhesive layer 340 is applied to the bonding surface 328 and the flexible member 314 is oriented so that the tensile surface 336 is coupled to the adhesive layer 340 and when the adhesive 340 is cured, a mechanical clamp (shown). No) can be used to hold the flexible member 314 in place. In one implementation, the adhesive layer 340 is cured for a predetermined period of time in an oven (not shown) at an elevated temperature. In this way, the composite component applied by mechanical clamping and pressurization of the flexible member 314 allows the first component 310 and the second component without additional pressure and / or costs associated with the autoclave molding procedure. Can be combined.

  FIG. 7 is an exploded view of an alternative joint assembly 400 used to assemble the fuselage assembly 200 (see FIG. 3), and FIG. 8 is a cross-sectional view of the joint assembly 400. In this implementation, the flexible member 314 is pressurized in a predetermined direction 364 before being coupled to the second component 320. Specifically, the flexible member 314 is bent away from the second component 320 to pressurize in a predetermined direction 364. The flexible member 314 then bends toward the second component 320 in a direction 366 opposite the predetermined direction 364 when the first component 310 and the second component are coupled together. Thus, the flexible member 314 that bends in the opposite direction 366 defines a compression surface 338 and a tensile surface 336 opposite the compression surface 338 in the first component 310. The compressed surface 338 is then coupled to the second component 320 via the adhesive layer 340.

  In one implementation, the flexible member 314 facilitates the determination of the peel position between the first component 310 and the second component 320 along the joint 330. For example, delamination can occur as a result of long-term use of the adhesive layer 340 and / or as a result of impact by foreign matter (not shown). Since the flexible member 314 is pressurized in the predetermined direction 364, the separation along the joint 330 causes the one or more flexible members 314 to move away from the second component 320 in the predetermined direction 364. Bends away from 320. Thus, the flexible member 314 that is disengaged from the second component 320 provides a visual indication of local delamination along the fitting 330 and / or allows delamination detection using non-destructive imaging techniques.

  The assemblies and methods described herein allow components to be coupled together in an efficient manner. Specifically, the assemblies described herein include a plurality of flexible members that extend from one component and connect to another component. These flexible members are, for example, pressurized in a predetermined direction that promotes an increased coupling load on the joint defined between them. In addition, by applying pressure to the flexible member in a direction away from other components, the position of separation along the joint can be easily determined. In this way, the flexible member facilitates improved control of the bond line when connecting the components together, and a simplified bonding process that can easily determine the location of the peel along the joint. Is possible.

  The description provided herein discloses the present invention, including the best mode, and allows those skilled in the art to practice the invention, including the creation and use of any equipment or system, and the implementation of any incorporated method. The example is used to make it possible. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other embodiments may have structural elements that do not deviate from the claimed language, or equivalent structural elements that have insignificant differences from the claimed language. If included, it is included within the scope of the claims.

200 Fuselage Assembly 210 First Cylindrical Section 212 First Cylindrical Section Body 214 First Cylindrical Section First End 216 First Cylindrical Section Second End 220 Second Cylindrical Section 222 Second Cylindrical Section Body 224 First end of second cylindrical section 226 Second end of second cylindrical section 230 Fitting 300 Fitting assembly 310 First component 312 First component first portion 314 First component multiple flexibility Sex member 316 first component one end 320 second component 322 second component first portion 324 second component plurality of flexible members 326 second component one end 328 coupling surface 330 joint 332 slit 334 Aperture 336 Tensile surface 338 Compressed surface 340 Adhesive layer 350 Longitudinal direction 352 Lateral direction 354 Predetermined direction 356 Direction opposite to predetermined direction 364 Predetermined direction 366 Direction opposite to predetermined direction 400 Joint assembly

Claims (13)

A second component comprising: a first component; a first portion; and a plurality of flexible members extending from the first portion, wherein the plurality of flexible members are arranged on the first component. Comprising the second component configured to bend when connecting the second component, to facilitate limiting the spread of edge separation beyond each of the plurality of flexible members ;
The plurality of flexible members are pressurized in a predetermined direction, and are configured to bend in a direction opposite to the predetermined direction when the second component is coupled to the first component. ing,
Fitting assembly.   The assembly of claim 1, wherein at least some of the plurality of flexible members are progressively thinner toward a reduced thickness tip of the second component.   The first component and the second component are each progressively thinner such that a joint defined between the first component and the second component has a substantially uniform thickness. Or the assembly according to 2. The assembly of claim 1 , wherein the plurality of flexible members are bent toward the first component and pressurized in the predetermined direction. The assembly according to claim 4 , wherein the plurality of flexible members bend in a direction opposite to the predetermined direction to apply a tensile force to the first component. The assembly of claim 1 , wherein the plurality of flexible members are bent away from the first component and pressurized in the predetermined direction. The assembly according to claim 6 , wherein the plurality of flexible members bend in a direction opposite to the predetermined direction to apply a compressive force to the first component. Wherein the plurality of flexible members, the are separated by a plurality of gaps defined between two adjacent each other of the flexible member, assembly according to any one of claims 1 to 7. 9. The assembly according to any one of claims 1 to 8 , wherein the plurality of flexible members are integrally formed with the first portion. A method of assembling the joint,
Providing a first component including a first portion and a plurality of flexible members extending from the first portion;
Connecting the plurality of flexible members to a second component, wherein the plurality of flexible members are configured to bend when connected to the second component; Connecting, making it easier to limit the spread of edge peeling beyond each of the sex members ;
Making it easier to determine the peeled portions of the plurality of flexible members by applying pressure to the plurality of flexible members in a predetermined direction which is a direction away from the second component;
Including methods. 11. The method of claim 10 , further comprising facilitating improved control of bond lines along the plurality of flexible members by pressurizing the plurality of flexible members in a predetermined direction toward the second component. The method described. Connecting the plurality of flexible members facilitates limiting separation of the edge beyond each of the plurality of flexible members by defining a gap between the plurality of flexible members. 12. The method according to any one of claims 10 or 11 , further comprising: The method of claim 12 , wherein defining a gap includes slitting an edge of the first component such that the plurality of flexible members are separated from each other.

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